US9341069B2 - Gas turbine - Google Patents

Gas turbine Download PDF

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Publication number
US9341069B2
US9341069B2 US13/239,549 US201113239549A US9341069B2 US 9341069 B2 US9341069 B2 US 9341069B2 US 201113239549 A US201113239549 A US 201113239549A US 9341069 B2 US9341069 B2 US 9341069B2
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US
United States
Prior art keywords
blade
gas turbine
rotor
recited
blade root
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US13/239,549
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English (en)
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US20120087782A1 (en
Inventor
Ruben Valiente
Shailendra Naik
Andre Saxer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
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Assigned to ALSTOM TECHNOLOGY LTD reassignment ALSTOM TECHNOLOGY LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NAIK, SHAILENDRA, SAXER, ANDRE, VALIENTE, RUBEN
Publication of US20120087782A1 publication Critical patent/US20120087782A1/en
Assigned to GENERAL ELECTRIC TECHNOLOGY GMBH reassignment GENERAL ELECTRIC TECHNOLOGY GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: ALSTOM TECHNOLOGY LTD
Application granted granted Critical
Publication of US9341069B2 publication Critical patent/US9341069B2/en
Assigned to ANSALDO ENERGIA IP UK LIMITED reassignment ANSALDO ENERGIA IP UK LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC TECHNOLOGY GMBH
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc

Definitions

  • the present invention relates to gas turbines.
  • cooling ducts are provided within the airfoil of the blades or vanes, which are supplied in operation with pressurised cooling air derived from the compressor part of the gas turbine.
  • the cooling ducts have the convoluted form of a serpentine, so that there is one flow of cooling fluid or cooling air passing through the airfoil in alternating and opposite directions.
  • such a convoluted passageway necessarily requires bends, which give rise to pressure losses without heat transfer.
  • FIGS. 1-3 Another problem recognized by the present invention, which is related to the supply of the cooling fluid through the root of the blade or vane, may be explained with reference to FIGS. 1-3 :
  • a blade 10 of a gas turbine comprises an airfoil 14 with a leading edge 17 and a trailing edge 16 .
  • the airfoil 14 extends along a longitudinal axis X of said blade between a lower end and a blade tip 15 .
  • a blade root 12 is provided for being attached to a groove 31 in a rotor 11 of said gas turbine.
  • a hollow blade core 18 is arranged within said airfoil 14 and extends along the longitudinal axis X between said blade root 12 and said blade tip 1 .
  • the blade core 18 is provided for the flow of a cooling fluid, which enters said blade core 18 through a blade inlet 20 at said blade root 12 and exits said blade core 18 through at least one dust hole at said blade tip 15 .
  • the cooling fluid (cooling air) is supplied by means of a rotor bore 19 , which runs through the rotor 11 and is in fluid communication with said blade inlet 20 of said blade 10 .
  • the direction of the rotor bore 19 is aligned with the blade orientation, i.e. the longitudinal axis X.
  • a unique passage smoothly distributes the flow all over the cross section of the duct further above the blade inlet 20 .
  • the area/shape of the rotor bore exit 19 which is cylindrical, and the inlet 20 of the blade, which is race-track shaped, are different, leading to a non-continuous interface (see FIG. 3 , the common area is shaded).
  • a gas turbine in an embodiment of the present invention, includes a rotor having a rotor groove and a rotor bore extending through the rotor, the rotor bore having a diffuser-shaped rotor bore exit.
  • a blade is attached to the rotor and includes a blade tip having at least one dust hole.
  • An airfoil has a leading edge and a trailing edge extending along a longitudinal axis of the blade between a lower end of the airfoil and the blade tip.
  • a blade root is disposed at the lower end of the airfoil and is configured to be removably disposed in the rotor groove.
  • the blade root includes a blade inlet having a cross sectional area that exceeds a cross sectional area of the rotor bore in at least one direction.
  • a hollow blade core is disposed in the airfoil and extends along the longitudinal axis of the blade between the blade root and the blade tip.
  • the blade core is configured to receive a cooling fluid from the rotor bore which is in fluid communication with the blade root at an interface between the rotor bore and the blade inlet.
  • a cross sectional area of the diffuser-shaped rotor bore exit covers the cross sectional area of the blade inlet at the interface and the cooling fluid enters the blade core through the blade inlet and exits the blade core through the at least one dust hole.
  • FIG. 1 shows a side view of a cooled rotor blade according to a first embodiment of a previous blade with a longitudinally extending rotor bore;
  • FIG. 2 shows a side view of a cooled rotor blade according to a second embodiment of a previous blade with an obliquely oriented rotor bore;
  • FIG. 3 shows the mismatch between the rotor bore exit and the blade inlet in a previous blade according to FIG. 1 or 2 ;
  • FIG. 4 shows a side view of a cooled rotor blade according to an embodiment of the invention with an obliquely oriented rotor bore comprising a diffuser-shaped rotor bore exit;
  • FIG. 5 shows in a side view a detail of the blade tip of a blade according to a second embodiment of the invention with a plurality of individually adjustable parallel cooling ducts;
  • FIG. 5 a shows a flow cross section of FIG. 5
  • FIG. 6 shows in a side view a detail of the blade root of the blade according to FIG. 5 with a bleeding interface plenum at the interface between the blade root and the bottom of the root-receiving rotor groove, including a focusing figure of the diffuser with the both angles ⁇ 1 and ⁇ 2 .
  • the problems recognized by the present invention in the blade design shown in FIGS. 1-3 include:
  • a gas turbine is provided with a cooled blade, which allows for a flexible design and rating of the cooling passages, and especially allows for a multi-pass design.
  • a rotor bore is provided with a diffuser-shaped rotor bore exit, such that the cross section area of the rotor bore exit at the interface between rotor bore and blade inlet covers the cross section area of the blade inlet.
  • an interface plenum is provided at the interface of said blade inlet and said rotor bore exit between the bottom surface of said blade root and the upper surface of said blade-root-receiving rotor groove, said interface plenum being designed to have a plenum bleed of cooling fluid to the outside of the blade root at the leading edge side or trailing edge side.
  • said blade root has a blade root height h in longitudinal direction
  • said blade core is split into a plurality of parallel cooling fluid ducts, wherein each of said cooling fluid ducts is in fluid communication with said blade inlet and has a dust hole at said blade tip, wherein a plurality of longitudinally extending not necessarily parallel webs is provided within said blade core for splitting said blade core into said plurality of cooling fluid ducts, and wherein, for an optimized cooling of said blade, an individual cross section area and an individual cooling fluid mass flow is associated with each of said plurality of cooling fluid ducts.
  • said individual cross section areas and/or said individual cooling fluid mass flows of said cooling fluid ducts are equal within ⁇ 25%.
  • said diffuser-shaped rotor bore exit has a diffuser angle ⁇ , consisting of the angles ⁇ 1 and ⁇ 2 .
  • the angular aperture of the both angles can be 7° ⁇ 1 ⁇ 13°, and 7° ⁇ 2 ⁇ 13°.
  • FIG. 4-6 several measures are taken ( FIG. 4-6 ), that substantially contribute to solve the problems/limitations described above:
  • an individual cross section area A 1 , A 2 , A 3 and an individual cooling fluid mass flow m 1 , m 2 , m 3 is associated with each of ducts 27 a , 27 b , 27 c .
  • the individual cross section areas A 1 , A 2 , A 3 and/or the individual cooling fluid mass flows m 1 , m 2 , m 3 of the ducts 27 a , 27 b , 27 c are chosen to be equal with each other within ⁇ 25%.
  • the diffuser-shaped rotor bore exit 24 has a diffuser angles ⁇ 1 and ⁇ 2 .
  • the blade root 12 has a blade root height h in longitudinal direction

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/239,549 2009-03-23 2011-09-22 Gas turbine Expired - Fee Related US9341069B2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP09155854 2009-03-23
EP09155854A EP2236746A1 (en) 2009-03-23 2009-03-23 Gas turbine
EP09155854.4 2009-03-23
PCT/EP2010/053670 WO2010108879A1 (en) 2009-03-23 2010-03-22 Gas turbine

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/053670 Continuation WO2010108879A1 (en) 2009-03-23 2010-03-22 Gas turbine

Publications (2)

Publication Number Publication Date
US20120087782A1 US20120087782A1 (en) 2012-04-12
US9341069B2 true US9341069B2 (en) 2016-05-17

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ID=40875154

Family Applications (1)

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US13/239,549 Expired - Fee Related US9341069B2 (en) 2009-03-23 2011-09-22 Gas turbine

Country Status (7)

Country Link
US (1) US9341069B2 (ko)
EP (2) EP2236746A1 (ko)
KR (1) KR101613866B1 (ko)
MX (1) MX340308B (ko)
RU (1) RU2531839C2 (ko)
SG (1) SG174494A1 (ko)
WO (1) WO2010108879A1 (ko)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11008872B2 (en) 2018-12-14 2021-05-18 Raytheon Technologies Corporation Extension air feed hole blockage preventer for a gas turbine engine
US11073024B2 (en) 2018-12-14 2021-07-27 Raytheon Technologies Corporation Shape recessed surface cooling air feed hole blockage preventer for a gas turbine engine
US11078796B2 (en) 2018-12-14 2021-08-03 Raytheon Technologies Corporation Redundant entry cooling air feed hole blockage preventer for a gas turbine engine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704716A1 (de) * 2011-03-22 2012-09-28 Alstom Technology Ltd Rotorscheibe für eine Turbine sowie Rotor und Turbine mit einer solchen Rotorscheibe.
EP2535515A1 (en) 2011-06-16 2012-12-19 Siemens Aktiengesellschaft Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade
EP2725191B1 (en) 2012-10-23 2016-03-16 Alstom Technology Ltd Gas turbine and turbine blade for such a gas turbine
WO2015088823A1 (en) * 2013-12-12 2015-06-18 United Technologies Corporation Gas turbine engine compressor rotor vaporization cooling
EP3059394B1 (en) * 2015-02-18 2019-10-30 Ansaldo Energia Switzerland AG Turbine blade and set of turbine blades
DE102016124806A1 (de) * 2016-12-19 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Turbinen-Laufschaufelanordnung für eine Gasturbine und Verfahren zum Bereitstellen von Dichtluft in einer Turbinen-Laufschaufelanordnung

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GB611044A (en) 1944-03-03 1948-10-25 Rateau Soc Improvements in or relating to wheels of turbines and the like machines
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2657902A (en) 1947-12-17 1953-11-03 Packard Motor Car Co Turbine rotor for turbojet engines
US2951340A (en) * 1956-01-03 1960-09-06 Curtiss Wright Corp Gas turbine with control mechanism for turbine cooling air
GB868788A (en) 1956-11-20 1961-05-25 Robert Pouit Improvements in gas turbine installations
US3370830A (en) * 1966-12-12 1968-02-27 Gen Motors Corp Turbine cooling
FR2152437A1 (ko) 1971-09-15 1973-04-27 Snecma
US3749514A (en) 1971-09-30 1973-07-31 United Aircraft Corp Blade attachment
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
US4177010A (en) * 1977-01-04 1979-12-04 Rolls-Royce Limited Cooled rotor blade for a gas turbine engine
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
JPS5951103A (ja) 1982-09-20 1984-03-24 Fuji Electric Co Ltd タ−ビン動翼及び円板の冷却装置
US4501053A (en) * 1982-06-14 1985-02-26 United Technologies Corporation Method of making rotor blade for a rotary machine
US4820122A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
EP0718467A1 (en) 1994-12-19 1996-06-26 General Electric Company Cooling of turbine blade tip
US5888049A (en) * 1996-07-23 1999-03-30 Rolls-Royce Plc Gas turbine engine rotor disc with cooling fluid passage
EP1041246A1 (de) 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
US20020090298A1 (en) 2000-12-22 2002-07-11 Alexander Beeck Component of a flow machine, with inspection aperture
US6735956B2 (en) * 2001-10-26 2004-05-18 Pratt & Whitney Canada Corp. High pressure turbine blade cooling scoop
US6874992B2 (en) 2001-11-27 2005-04-05 Rolls-Royce Plc Gas turbine engine aerofoil
US7059825B2 (en) * 2004-05-27 2006-06-13 United Technologies Corporation Cooled rotor blade
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RU2323343C2 (ru) 2006-03-20 2008-04-27 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") Охлаждаемая лопатка турбомашины
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
US7762774B2 (en) * 2006-12-15 2010-07-27 Siemens Energy, Inc. Cooling arrangement for a tapered turbine blade

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB611044A (en) 1944-03-03 1948-10-25 Rateau Soc Improvements in or relating to wheels of turbines and the like machines
US2657902A (en) 1947-12-17 1953-11-03 Packard Motor Car Co Turbine rotor for turbojet engines
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2951340A (en) * 1956-01-03 1960-09-06 Curtiss Wright Corp Gas turbine with control mechanism for turbine cooling air
GB868788A (en) 1956-11-20 1961-05-25 Robert Pouit Improvements in gas turbine installations
US3370830A (en) * 1966-12-12 1968-02-27 Gen Motors Corp Turbine cooling
FR2152437A1 (ko) 1971-09-15 1973-04-27 Snecma
US3749514A (en) 1971-09-30 1973-07-31 United Aircraft Corp Blade attachment
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
US4177010A (en) * 1977-01-04 1979-12-04 Rolls-Royce Limited Cooled rotor blade for a gas turbine engine
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
US4501053A (en) * 1982-06-14 1985-02-26 United Technologies Corporation Method of making rotor blade for a rotary machine
JPS5951103A (ja) 1982-09-20 1984-03-24 Fuji Electric Co Ltd タ−ビン動翼及び円板の冷却装置
US4820122A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
EP0718467A1 (en) 1994-12-19 1996-06-26 General Electric Company Cooling of turbine blade tip
US5888049A (en) * 1996-07-23 1999-03-30 Rolls-Royce Plc Gas turbine engine rotor disc with cooling fluid passage
EP1041246A1 (de) 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
US6565318B1 (en) 1999-03-29 2003-05-20 Siemens Aktiengesellschaft Cast gas turbine blade through which coolant flows, together with appliance and method for manufacturing a distribution space of the gas turbine blade
US20020090298A1 (en) 2000-12-22 2002-07-11 Alexander Beeck Component of a flow machine, with inspection aperture
US6735956B2 (en) * 2001-10-26 2004-05-18 Pratt & Whitney Canada Corp. High pressure turbine blade cooling scoop
US6874992B2 (en) 2001-11-27 2005-04-05 Rolls-Royce Plc Gas turbine engine aerofoil
US7264445B2 (en) * 2003-07-12 2007-09-04 Alstom Technology Ltd Cooled blade or vane for a gas turbine
US7059825B2 (en) * 2004-05-27 2006-06-13 United Technologies Corporation Cooled rotor blade
US7097419B2 (en) * 2004-07-26 2006-08-29 General Electric Company Common tip chamber blade
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
RU2323343C2 (ru) 2006-03-20 2008-04-27 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") Охлаждаемая лопатка турбомашины
US7762774B2 (en) * 2006-12-15 2010-07-27 Siemens Energy, Inc. Cooling arrangement for a tapered turbine blade

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European Patent Office, Extended European Search Report in European Patent Application No. 09 15 5854 (Jul. 30, 2009).
European Patent Office, International Search Report in International Patent Application No. PCT/EP2010/053670 (May 25, 2010).
Office Action (Decision on Grant) issued on Jun. 17, 2014, by the Russian Patent Office in corresponding Russian Application No. 2011142732, and an English Translation of the Office Action. (11 pages).
Office Action issued on Mar. 20, 2015, by the Korean Patent Office in corresponding Korean Application No. 10-2011-7022161, and an English Translation of the Office Action.
Russian Office Action issued in corresponding Russian Application No. 2011142732 dated Dec. 26, 2013 with translation.
Zhirickij et al ., "Gazovye turbiny aviacionnyh dvigatelej", Moscow, oborongiz, 1963, p. 378, fig. 9.29.

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11008872B2 (en) 2018-12-14 2021-05-18 Raytheon Technologies Corporation Extension air feed hole blockage preventer for a gas turbine engine
US11073024B2 (en) 2018-12-14 2021-07-27 Raytheon Technologies Corporation Shape recessed surface cooling air feed hole blockage preventer for a gas turbine engine
US11078796B2 (en) 2018-12-14 2021-08-03 Raytheon Technologies Corporation Redundant entry cooling air feed hole blockage preventer for a gas turbine engine

Also Published As

Publication number Publication date
KR101613866B1 (ko) 2016-04-20
RU2011142732A (ru) 2013-04-27
RU2531839C2 (ru) 2014-10-27
WO2010108879A1 (en) 2010-09-30
SG174494A1 (en) 2011-10-28
KR20120005444A (ko) 2012-01-16
EP2411629A1 (en) 2012-02-01
MX340308B (es) 2016-07-05
MX2011009617A (es) 2011-09-29
US20120087782A1 (en) 2012-04-12
EP2236746A1 (en) 2010-10-06
EP2411629B1 (en) 2018-03-07

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